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Abstract:

The technology can include a retractable rotary turret system. The system
includes a base comprising two support arms. The system further includes
a turret platform that is a truncated sphere having a substantially flat
side and a substantially spherical side. The turret platform includes a
turret support ring rotary coupled to the two support arms and a turret
device isolatively coupled to the turret support ring. The turret
platform is rotatable along a first dimension for deployment of the
spherical side and is rotatable along the first dimension for deployment
of the flat side.

Claims:

1. A retractable rotary turret system, the system comprising: a base
comprising two support arms; a turret platform that is a truncated sphere
having a substantially flat side and a substantially spherical side, the
turret platform comprising: a turret support ring rotary coupled to the
two support arms; and a turret device isolatively coupled to the turret
support ring; wherein the turret platform is rotatable along a first
dimension for deployment of the spherical side and is rotatable along the
first dimension for deployment of the flat side.

2. The system of claim 1, wherein the turret device comprises: a mirror
drive assembly having a primary window in the spherical side of the
turret platform; and a coarse tracker assembly having a secondary window
in the spherical side of the turret platform.

3. The system of claim 2, wherein a center axis of the primary window is
off-set and parallel to a center axis of the secondary window.

4. The system of claim 2, wherein a center axis of the mirror drive
assembly is off-set and parallel to a center axis of the turret platform.

5. The system of claim 2, wherein the primary window and the secondary
window are curved to conform to an outer surface of the spherical side.

6. The system of claim 2, wherein the primary window and the secondary
window are substantially flat.

7. The system of claim 1, further comprising: a first mirror mounted
within the base and for receiving optical energy from an optical energy
system; a second mirror mounted within a top portion of the first support
arm for receiving the optical energy from the first mirror and for
directing the optical energy along an axis parallel to the first support
arm; a third mirror mounted within a bottom portion of the first support
arm for receiving the optical energy from the second mirror and for
directing the optical energy through an opening in the turret platform; a
fourth mirror mounted within the turret platform for receiving the
optical energy from the third mirror and directing the optical energy to
the turret device; a secondary mirror mounted within the turret device
for receiving the optical energy from the fourth mirror and for expanding
the optical beam path from the fourth mirror; and a primary mirror
mounted with the turret device for receiving the optical energy from the
secondary mirror and recollimating or focusing the optical energy based
on a beam application.

8. The system of claim 7, wherein the beam application is a sensing
application and the telescope collimates the optical energy based on a
target range.

9. The system of claim 7, wherein the beam application is a high energy
weapon application and the primary mirror focuses the optical energy onto
a target.

10. The system of claim 1, wherein the turret device comprises a high
energy laser pointing and tracking system, wherein the high energy laser
pointing and tracking system is usable during deployment of the spherical
side of the turret platform.

11. The system of claim 1, wherein the turret device comprises a passive
optical sensor for providing imagery in one or more spectral bands in
visible and infrared regions.

12. The system of claim 1, wherein the turret device comprises a
semi-active sensor for providing range finding or illuminated target
tracking

13. The system of claim 1, wherein the turret platform is rotatable along
two axes, the first axis for deployment and aiming of the turret device,
and the second axis for aiming of the turret device.

14. The system of claim 1, wherein the turret platform geometry is
defined as a2=b(2R-b), wherein: a is 1/2 of a maximum span of a
circular footprint of the stowed side of the turret platform flush with
an external surface of a vehicle; b is a maximum height of the spherical
side when deployed from the vehicle; and R is a radius of the turret
platform.

15. A truncated sphere turret platform, the turret platform comprising: a
turret support ring rotary rotatable along an elevation axis; and a
turret device isolatively coupled to the turret support ring; wherein the
turret platform having a flat side and a spherical side, and wherein the
turret platform is rotatable along the elevation axis for deployment of
the spherical side and is rotatable along the elevation axis for
deployment of the flat side.

16. The turret platform of claim 15, wherein the turret device comprises
an off-axis telescope with a spherical mirror, a figure mirror, a conic
mirror, an on-axis telescope with central obscuration, a refractive
telescope, or any combination thereof.

17. The turret platform of claim 15, wherein the turret platform
comprising a plurality of apertures in the deployed side of the turret
platform.

18. The turret platform of claim 15, wherein the turret device
comprising: a mirror drive assembly having a primary window in the
spherical side of the turret platform; and a coarse tracker assembly
having a secondary window in the spherical side of the turret platform,
wherein the primary window and the secondary window are mounted
side-by-side in the spherical side of the turret platform.

19. A turret payload system, the system comprising: a payload support
ring rotary coupled to two support arms; and a payload device isolatively
coupled to the payload support ring; and a payload windscreen shell in a
shape of a truncated sphere having a substantially flat side and a
substantially spherical side on opposite sides of each other; wherein the
turret payload system is rotatable along the elevation axis over a first
dimension for deployment of the spherical side and is rotatable over a
second dimension for deployment of the flat side.

20. The turret payload system of claim 19, wherein the substantially flat
side of the payload windscreen shell substantially conforms to a vehicle
surface when stowed.

21. The turret payload system of claim 19, wherein the substantially
spherical side of the payload windscreen shell provides a minimum
protrusion outside a vehicle and maintains a maximum field of regard when
deployed.

Description:

BACKGROUND

[0001] Beam delivery systems (e.g., sensor beam, laser beam, etc.) have
generally been mounted in pods on the exterior of an aircraft, such as an
unmanned aerial vehicle, a helicopter, or a fixed wing aircraft. Stowing
mechanisms and features are generally used on the pod to protect the
primary windows of the beam delivery system during take-off and landing
of the aircraft. The pod itself generally remains outside the aircraft in
the windstream. Typically, when the entire system must be protected,
deployment mechanisms are used to move the turret from a storage bay of
the aircraft into the windstream. With these mechanisms the storage bay
volume is empty during system deployment, but the storage bay cannot be
used for other components due to the need of the space during system
retraction. In other configurations of the system, the predominant axis
is roll, with azimuth and elevation gimbals nestled within the roll
windscreen. In these configurations, the forward look angle is limited to
the window length and, generally, cannot be extended to near forward look
angles.

[0002] In other designs of the system, an on-axis telescope is utilized
with an auto-alignment system to align the sensor system and/or beam
delivery system with a target. The use of the on-axis telescope
simplifies the auto-alignment system. However, a central obscuration
created by a secondary mirror results in a matching hole in the output
beam. The on-axis telescope configuration, generally, does not operate
correctly for beam systems that produce a solid beam profile with no
central obscuration. An off-axis, unobscured telescope for the beam
delivery system overcomes this problem.

[0004] One approach provides a retractable rotary turret system. The
system includes a base comprising two support arms. The system further
includes a turret platform that is a truncated sphere having a
substantially flat side and a substantially spherical side. The system
further includes a turret support ring rotary coupled to the two support
arms. The system further includes a turret device isolatively coupled to
the turret support ring. The turret platform is rotatable along a first
dimension for deployment of the spherical side and is rotatable along the
first dimension for deployment of the flat side.

[0005] Another approach provides a truncated sphere turret platform. The
turret platform includes a turret support ring rotary rotatable along an
elevation axis. The turret platform further includes a turret device
isolatively coupled to the turret support ring. The turret platform has a
flat side and a spherical side. The turret platform is rotatable along
the elevation axis for deployment of the spherical side and is rotatable
along the elevation axis for deployment of the flat side.

[0006] Another approach provides a turret payload system. The system
includes a payload support ring rotary coupled to two support arms. The
system further includes a payload device isolatively coupled to the
payload support ring. The system further includes a payload windscreen
shell in a shape of a truncated sphere having a substantially flat side
and a substantially spherical side on opposite sides of each other. The
turret payload system is rotatable along the elevation axis over a first
dimension for deployment of the spherical side and is rotatable over a
second dimension for deployment of the flat side.

[0007] Another approach provides a high power laser beam delivery system.
The system includes a rotary turret platform rotatable along multiple
axes for aiming of a high power laser beam. The system further includes a
turret payload device coupled to the rotary turret platform that is a
truncated sphere and configured to rapidly deploy from a vehicle and stow
within the vehicle. The system further includes at least two conformal
windows in a spherical side of the turret payload device. The system
further includes an off-axis telescope coupled to the turret payload
device, having an articulated secondary mirror for correcting optical
aberrations, and configured to reflect the high power laser beam to a
target through the first of the at least two conformal windows. The
system further includes an illuminator beam device coupled to the turret
payload device and configured to detect atmospheric disturbance between
the system and the target by actively illuminating the target to generate
a return aberrated wavefront through the first of the at least two
conformal windows. The system further includes a coarse tracker coupled
to the turret payload device, positioned parallel to and on an axis of
revolution of the off-axis telescope, and configured to detect, acquire,
and track the target through the second of the at least two conformal
windows.

[0008] Another approach provides a rotary turret system. The system
includes a base comprising two support arms; a first rotating mechanism
within the base configured to rotate the base perpendicular to a nominal
direction of flight of a vehicle; a Coude path configured to provide a
path for a high energy laser beam from the base via the first support arm
to a target; a second rotating mechanism in at least one of the two
support arms and configured to rotate the base perpendicular to an
azimuth axis of the base; and one or more fast steering mirrors
configured to maintain proper beam location and orientation of the high
energy laser beam through the Coude path to the target.

[0009] In other examples, any of the approaches above can include one or
more of the following features.

[0010] In some examples, the turret device includes a mirror drive
assembly having a primary window in the spherical side of the turret
platform and a coarse tracker assembly having a secondary window in the
spherical side of the turret platform.

[0011] In other examples, a center axis of the primary window is off-set
and parallel to a center axis of the secondary window.

[0012] In some examples, a center axis of the mirror drive assembly is
off-set and parallel to a center axis of the turret platform.

[0013] In other examples, the primary window and the secondary window are
curved to conform to an outer surface of the spherical side.

[0014] In some examples, the primary window and the secondary window are
substantially flat.

[0015] In other examples, the system further includes a first mirror
mounted within the base and for receiving optical energy from an optical
energy system; a second mirror mounted within a top portion of the first
support arm for receiving the optical energy from the first mirror and
for directing the optical energy along an axis parallel to the first
support arm; a third mirror mounted within a bottom portion of the first
support arm for receiving the optical energy from the second mirror and
for directing the optical energy through an opening in the turret
platform; a fourth mirror mounted within the turret platform for
receiving the optical energy from the third mirror and directing the
optical energy to the turret device; a secondary mirror mounted within
the turret device for receiving the optical energy from the fourth mirror
and for expanding the optical beam path from the fourth mirror; and a
primary mirror mounted with the turret device for receiving the optical
energy from the secondary mirror and recollimating or focusing the
optical energy based on a beam application.

[0016] In some examples, the beam application is a sensing application and
the telescope collimates the optical energy based on a target range.

[0017] In other examples, the beam application is a high energy weapon
application and the primary mirror focuses the optical energy onto a
target.

[0018] In some examples, the turret device includes a high energy laser
pointing and tracking system, wherein the high energy laser pointing and
tracking system is usable during deployment of the spherical side of the
turret platform.

[0019] In other examples, the turret device includes a passive optical
sensor for providing imagery in one or more spectral bands in visible and
infrared regions.

[0020] In some examples, the turret device includes a semi-active sensor
for providing range finding or illuminated target tracking

[0021] In other examples, the turret platform is rotatable along two axes,
the first axis for deployment and aiming of the turret device, and the
second axis for aiming of the turret device.

[0022] In some examples, the turret platform geometry is defined as
a2=b(2R-b), wherein a is 1/2 of a maximum span of a circular
footprint of the stowed side of the turret platform flush with an
external surface of a vehicle; b is a maximum height of the spherical
side when deployed from the vehicle; and R is a radius of the turret
platform.

[0023] In other examples, the turret device includes an off-axis telescope
with a spherical mirror, a figure mirror, a conic mirror, an on-axis
telescope with central obscuration, and/or a refractive telescope.

[0024] In some examples, the turret platform includes a plurality of
apertures in the deployed side of the turret platform.

[0025] In other examples, the turret device includes a mirror drive
assembly having a primary window in the spherical side of the turret
platform; and a coarse tracker assembly having a secondary window in the
spherical side of the turret platform. The primary window and the
secondary window are mounted side-by-side in the spherical side of the
turret platform.

[0026] In some examples, the substantially flat side of the payload
windscreen shell substantially conforms to a vehicle surface when stowed.

[0027] In other examples, the substantially spherical side of the payload
windscreen shell provides a minimum protrusion outside a vehicle and
maintains a maximum field of regard when deployed.

[0028] In some examples, the spherical side is substantially spherical.

[0029] In other examples, the at least two conformal windows are
substantially spherical, and/or substantially flat.

[0030] In some examples, when stowed, the turret payload device conforms
to an outer surface of the vehicle for maintaining at least one low
observability characteristic of the vehicle.

[0031] In other examples, the system further includes an auto-alignment
system configured to communicate commands to the articulated secondary
mirror configured to modify aiming of the high power laser beam and to
one or more fast steering mirrors configured to modify the aiming of the
high power laser beam.

[0032] In some examples, the system further includes a wavefront error
sensor coupled to the turret payload device and configured to determine
an induced distortion of the aberrated wavefront of the returning
illuminator beam from the target based on a beam quality metric for the
target.

[0033] In other examples, the wavefront error sensor is further configured
to communicate commands to the articulated secondary mirror based on the
determined induced distortion to reduce large, low order wavefront
aberrations.

[0034] In some examples, the wavefront error sensor is further configured
to communicate commands to the articulated secondary mirror based on the
determined induced distortion to reduce residual tilts of the high power
laser beam.

[0035] In other examples, the system further includes an inertial
measurement unit configured to detect errors from one or more commands
communicated to the turret payload device based on an actual turret
position and one or more fast steering mirrors coupled to the turret
payload device and configured to modify aiming of the high power laser
beam based on the detected errors.

[0036] In some examples, the turret payload device further includes a
payload support ring rotary coupled to two support arms; a payload device
isolatively coupled to the payload support ring; and a payload windscreen
shell in a shape of a truncated sphere having a flat side and a spherical
side on opposite sides of each other. The turret payload system is
rotatable along the elevation axis over a first dimension for deployment
of the spherical side and is rotatable over a second dimension for
deployment of the flat side.

[0037] The techniques described herein can provide one or more of the
following advantages. An advantage of the technology is that the turret
system or parts thereof are rotatable along a single dimension for
deployment of the spherical side and the flat side of the turret system,
thereby eliminating the need to translate the azimuth base of the turret
system. Another advantage of the technology is that the deployment time
of the turret system for the single dimension rotation for deployment is
reduced to that of the axis rotation speed, thereby decreasing the
deployment time. Another advantage of the technology is that the single
dimension deployment of the turret system advantageously reduces the dead
space in the deployment vehicle (e.g., aircraft cargo bay), thereby
maximizing the volume available for other components. Another advantage
of the technology is the use of conformal apertures (i.e., windows in the
turret system) for the spherical side of the turret system advantageously
provides a consistent spherical shape in the airflow around the
deployment vehicle, thereby maximizing the correction of aero-optic
wavefront error (WFE) distortions and torque disturbances on the outer
parts of the turret system.

BRIEF DESCRIPTION OF THE DRAWINGS

[0038] The foregoing and other objects, features and advantages will be
apparent from the following more particular description of the
embodiments, as illustrated in the accompanying drawings in which like
reference characters refer to the same parts throughout the different
views. The drawings are not necessarily to scale, emphasis instead being
placed upon illustrating the principles of the embodiments.

[0039]FIG. 1 is a diagram of an exemplary beam deployment environment;

[0040] FIG. 2A is a diagram of an exemplary deployed payload device;

[0041] FIG. 2B is a diagram of an exemplary stowed payload device;

[0042] FIG. 3A is a side view of a diagram of an exemplary stowed turret
system;

[0043] FIG. 3B is a perspective diagram of the stowed turret system of
FIG. 3A;

[0044]FIG. 4A is a side view of a diagram of an exemplary deployed turret
system;

[0045] FIG. 4B is a perspective diagram of the deployed turret system of
FIG. 4A;

[0046] FIG. 4C is another perspective diagram of the deployed turret
system of FIG. 4A;

[0047] FIG. 5A is a sectional diagram of another exemplary deployed turret
system;

[0048] FIG. 5B is a sectional diagram of another exemplary deployed turret
system;

[0051] A retractable rotary turret and/or rapidly deployable high energy
laser beam delivery system includes technology that, generally, provides
a rapidly deployable turret system (e.g., a truncated sphere, a rounded
protrusion, a rotating platform, etc.) that can be used with a deployment
vehicle (e.g., low observability aircraft, aircraft, tank, helicopter,
etc.) for delivery of a beam. The technology for rapid deployment of the
mechanisms can be utilized to deliver the beam (e.g., laser beam, light
beam, sensor beam, etc.) to a target. The technology enables sensitive
components of the beam delivery system (e.g., sensor, telescope, window,
etc.) to be protected during selected movements by the deployment vehicle
(e.g., take-off and/or landing of an aircraft, movement of a tank through
a forest, etc.) and rapidly deployed for beam delivery (e.g., two second
deployment, etc.).

[0052] The technology can provide for deployment via a rotary motion of
the turret system. The technology eliminates a design problem associated
with the elevator mechanism of a turret system by replacing the vertical
translation of an elevator with the simple motion of a turret ball
rotating on its elevation axis to go from the stowed position to the
deployed position, thereby advantageously increasing the efficiency of
the deployment mechanism. The simple motion of the turret ball rotating
on its elevation axis advantageously reduces the risk of damage caused to
accidental deployment or stowing of the turret ball. In other words, the
technology deploys and stows the turret system by rotating the turret
system in a single dimension, thereby advantageously decreasing the time
required for deployment (e.g., less than one second, less than five
seconds, etc.) and reducing the forces exerted on the deployment vehicle.
The deployment and stowing of the technology via the single dimension
advantageously enables the technology is secured to the same base whether
deployed or stowed, thereby increasing the rigidly of the technology.

[0053] The technology can provide a minimal protrusion of the deployed
turret system from the vehicle while maintaining a maximum field of
regard when deployed. When deployed, a small part of the spherical turret
system is exposed to the air stream around the deployment vehicle,
thereby advantageously reducing the tendency for wind buffeting to affect
the optical line of sight (LOS) of the beam. When stowed, the turret
system is flush with the outside contour of the deployment vehicle,
thereby eliminating the necessity of a separate door or cover. The
arrangement of the stowed side can enable the deployment vehicle to
maintain various vehicle characteristics (e.g., low-profile, stealth,
etc.). Another advantage of the one dimension deployment and stowing is
that the beam can be kept in fully operational mode when stowed without
risk of inadvertently hitting a deployment cover.

[0054]FIG. 1 is a diagram of an exemplary beam deployment environment
100. The environment 100 illustrates an aircraft 110 with a rotary turret
system 112 and a target 120 (in this example, a tank 120). The rotary
turret system 112 directs a beam 114 onto the target 120. The beam 114
can be, for example, utilized by a sensor and/or laser beam system within
the aircraft 110 to track the target 120 and/or damage/destroy the target
120.

[0055] FIG. 2A is a diagram of an exemplary deployed payload device 200a.
The payload device 200a is deployed from a deployment vehicle (not
shown). The deployment vehicle can, for example, include an aircraft
(e.g., helicopter, fixed wing aircraft, etc.), a tank, a train, an
automobile, and/or any other type of transportation device. As
illustrated in FIG. 2A, the payload device 200a is deployed from the
deployment vehicle through the vehicle's skin 230 (in this example, the
aircraft skin 230). The aperture diameter in the vehicle's skin is 2a
(210), which is the length of a substantially flat side 240 of the
payload device 200a. The payload device 200a includes a primary window
220 (in this example, a laser window 220). The payload device 200a and
the primary window 220 can be utilized to direct various types of beams
(e.g., high energy laser beam, sensor beam, infrared sensor beam, etc.)
to a target.

[0056] As illustrated in FIG. 2A, the payload device 200a is a truncated
sphere having a substantially flat side 240 (e.g., 100% flat, sloped at 1
degree angle, etc.) and a substantially spherical side 250 (e.g., 100%
round, 98% round, etc.). The payload device 200a advantageously provides
a large field of regard with a minimum exposed turret surface, thereby
maximizing the active operating region while minimizing airflow
turbulence. The payload device 200a advantageously provides a single
rotation axis for deployment and stowing, thereby removing turret
translation (i.e., vertical movement) and providing a built-in door
(i.e., the flat side 240 of the payload device 200a) that conforms to the
outer skin of the deployment vehicle.

[0057] In some examples, the primary window 220 and a secondary window
(not shown) are conformal windows (e.g., substantially spherical,
substantial flat, combination of spherical and flat, etc.) within the
payload device 200a to maintain the spherical shape of the exposed
turret, thereby reducing the frontal cross-sectional area and the
associated aero-optic issues resulting from airflow turbulence. The
reduction of the airflow turbulence advantageously reduces jitter,
increases pointing accuracy, and/or minimizes the impact of the
aerodynamics on the deployment vehicle.

[0058] The truncated sphere has a radius R with a portion of the sphere
cut off (also referred to as the flat side 240). A circular section is
through the center of the ball and the horizontal x-axis of the section
parallel to the longitudinal axis of the deployment vehicle. The circular
section is in the x-y plane of the sphere, with the out-of-plane z-axis
defining the elevation axis and the y-axis as the azimuth axis; the pivot
point is the center of the sphere, at the origin of the three axes.
Referring to this circular section, the dashed arc segment is cut off;
the length of the chord (also referred to as the flat side 240) is
defined as 2a. The distance from the radius R to the chord of the
truncated sphere is b. The distance from the center of the sphere to the
chord is (R-b). The relationship between a, b, and R is in accordance
with: a2=b(2R-b); wherein a=1/2 of a maximum span of a circular
footprint of the stowed side of the turret platform with an external
surface of the vehicle; b is a maximum height of the spherical side when
deployed from the vehicle; and R is the radius of the turret platform.
The distance from the pivot point to the bottom cutout is (R-b).

[0059] FIG. 2B is a diagram of an exemplary stowed payload device 200b.
The stowed payload device 200b includes the same components as described
above with respect to FIG. 2A. As illustrated in FIG. 2B, the payload
device 200b is in a stowed position. In other words, the spherical side
250 is protected within the body of the deployment vehicle (e.g.,
aircraft cargo bay, car body, etc.) and the flat side 240 conforms to the
skin 230 of the deployment vehicle. In some examples, the flat side 240
conforms to the skin 230 of the deployment vehicle to maintain at least
one low observability characteristic of the deployment vehicle (e.g.,
stealth, low profile, etc.). The stowage of the payload device 200b
within the body of the deployment vehicle and/or exposure of the flat
side 240 to the environment advantageously protects the payload device
200b from damage.

[0060] FIG. 3A is a side view of a diagram of an exemplary stowed turret
system 300. FIG. 3B is a perspective view of the turret system 300 of
FIG. 3A. The turret system 300 includes a base 310 and two supporting
arms 320 (second supporting arm is not shown). A flat side 340 of the
turret system 300 conforms to an outer surface 330 of a deployment
vehicle (not shown). The conformance to the outer surface 330 of the
deployment vehicle advantageously enables the turret system 300 to
maintain characteristics of the deployment vehicle while simplifying the
deployment mechanism.

[0061]FIG. 4A is a side view of a diagram of an exemplary deployed turret
system 400. FIG. 4B is a diagram of another view of the turret system 400
of FIG. 4A. FIG. 4C is a diagram of another perspective view of the
turret system 400 of FIG. 4A. The turret system 400 includes a base 410,
two supporting arms 420, and a turret platform 440. The turret platform
440 is a truncated sphere with a substantially flat side 444 and a
substantially spherical side 442. As illustrated in FIG. 4A, the
spherical side 442 of the turret platform 440 extends from an outer
surface 430 of a deployment vehicle (not shown). The spherical side 442
of the turret platform 440 includes a primary window 450 and a secondary
window 460. The primary window 450 can be utilized by a beam delivery
assembly and the secondary window 460 can be utilized by a coarse tracker
assembly. The beam delivery assembly and the coarse tracker assembly can,
for example, be utilized to direct (e.g., recollimate, focus, etc.)
optical energy (e.g., laser beam, sensor beam, etc.) based on a beam
application.

[0062] In some examples, a center axis of the primary window 450 is
off-set and parallel to a center axis of the secondary window 460. The
off-set and parallel configuration (e.g., side-by-side mounting) of the
primary window 450 and the secondary window 460 enables the beam and the
tracking beam to converge on a target and maximize lookdown angle for the
deployed turret system 400. The off-set and parallel configuration of the
primary window 450 and the secondary window 460 can minimize the minimum
ball diameter advantageously, thereby enabling the technology to be
packaged in small tactical flight volumes. In other examples, a center
axis of the mirror drive assembly is off-set and parallel to a center
axis of the turret platform 440. The off-set and parallel configuration
(e.g., side-by-side mounting) of the primary window 450 and the secondary
window 460 enables the beam and the tracking beam to converge on a target
and maximize lookdown angle for the deployed turret system 400 and be
compatible with an off-axis auto-alignment system.

[0063] In some examples, the primary window 450 and/or the secondary
window 460 are curved to conform to the outer surface of the spherical
side 442 of the turret platform 440. The curvature of the primary window
450 and the secondary window 460 can enable the turret system 400 to
advantageously reduce air turbulence and minimize turret vibration. In
other examples, the primary window 450 and/or the secondary window 460
are substantially spherical (e.g., 99% spherical, 97% spherical, etc.),
substantially flat (e.g., wedged at 1%, concave, etc.), and/or
substantially aspherical. The flat parts of the primary window 450 and
the secondary window 460 can reduce the deflections of the beams, thereby
decreasing the complexity of the alignment and beam mechanisms.

[0064] The beam application can be usable during deployment of the
spherical side of the turret system 400. In some examples, the beam
application is active during stowing of the spherical side of the turret
system 400 and is rapidly deployable for use (e.g., range finding, target
tracking, etc.). In other examples, the beam application is a sensing
application, a high energy weapon application, a high energy laser
pointing and tracking system, a passive optical sensor, a semi-active
sensor, and/or any other type of beam application.

[0065] FIG. 5A is a sectional diagram of another exemplary deployed turret
system 500a. The turret system 500a includes a primary mirror 540 and a
telescope 550. The telescope 550 is isolatively mounted to the turret
system 500 in such a manner as to minimize the effects of mechanical
and/or structural deflection of the turret system 500 that can adversely
affect the LOS of the telescope 550. The primary mirror 540 is mounted to
the telescope 550 and recollimates or focuses optical energy based on the
beam application. As illustrated in FIG. 5A, the turret system 500a has a
laser beam diameter D1 564a and a lookdown angle A1 562a. The lookdown
angle A1 562a is the smallest lookdown angle A1 562a for the output beam
diameter D1 564a.

[0066] FIG. 5B is a sectional diagram of another exemplary deployed turret
system 500b. As illustrated in FIG. 5B, the turret system 500b has a
laser beam diameter D2 564b and a lookdown angle B1 562b. The lookdown
angle B1 562b is the smallest lookdown angle B1 562b for the output beam
diameter D2 564b. As illustrated in FIGS. 5A and 5B, the lookdown angle
A1 562a to A2 562b is reduced by reducing the laser beam diameter D1 564a
to D2 564b.

[0067] FIGS. 6A-6D are diagrams of exemplary deployed turret systems 600a,
600b, 600c, and 600d (generally referred to as turret system 600). FIG.
6A illustrates deployment of a turret platform of the turret system 600a.
FIG. 6B illustrates deployment of the turret platform of the turret
system 600b in a nadir position. FIG. 6C illustrates 180° rotation
along an azimuth axis of the turret platform of the turret system 600c
from the position illustrated in FIG. 6B while remaining in the nadir
position. FIG. 6D illustrates deployment of the turret platform of the
turret system 600d in an elevated position to a stop-limit (e.g., the
minimum lookdown angle for the turret system 600d configuration).

[0068] FIGS. 6A-6D illustrate a field of regard (FOR) for the turret
systems 600. The FOR can be the range of operation of a beam
incorporating a Coude path optical design. In other examples, for a
passive imaging system, the turret system 600 utilizes an internal fold
mirror prior to the window to provide forward line of sight (LOS) at a
zero angle of depression. In some examples, the turret system 600
includes a passive optical sensor for providing imagery in one or more
spectral bands in visible and infrared regions. In other examples, the
turret system 600 includes a semi-active sensor for providing range
finding or illuminated target tracking

[0069] FIGS. 7A-7B are diagrams of an exemplary laser beam delivery system
700 from different views. The system 700 includes a turret platform 702,
a turret payload device 706, an off-axis telescope 715, an illuminator
beam device (not shown), a coarse tracker 745, an auto-alignment system
735, a wavefront error sensor (not shown), an inertial measurement unit
(IMU) 760, and fast steering mirrors 710 and 765. The turret payload
device 706 incorporates two conformal windows 707 and 708. The turret
payload device 706 includes a payload support ring 720, two support arms
703a and 703b, and a payload windscreen shell 721 and 722. The turret
platform 702, the turret support arms 703a and 703b, and the turret
payload device 706 can be, for example, referred to as "the turret". The
laser beam delivery system 700 with the roll-over design of the turret
payload device 706 enables the technology to be continuously active since
the technology has a constant base rigidity without risk of causing
issues with the technology (e.g., unusual mode of operation, discharge of
technology, etc.), thereby increasing the deployable environments for the
technology.

[0070] The turret platform 702 provides the mechanical interface between
the system 700 and the vehicle (not shown). The two support arms 703a and
703b are attached to the turret platform 702 and are rotatable along a
first axis for aiming a high power laser beam and/or any other type of
beam (e.g., sensor beam, infrared beam, etc.). For example, the support
arms 703a and 703b are rotatable along a first axis for aiming of the
turret payload device 706. The turret payload device 706 is coupled to
the turret platform 702 (e.g., direct connection mechanism, isolated
indirect connection mechanism to minimize vibrations, etc.). The turret
payload device 706 is a truncated sphere with a spherical side and a flat
side. The turret payload device 706 is configured to be rapidly
deployable (e.g., within one second, within two seconds, etc.) from a
vehicle (not shown) and rapidly stowable (e.g., within 1.5 seconds,
within two seconds, etc.) within the vehicle.

[0071] The two conformal windows 707 and 708 are in the spherical side of
the turret payload device 706. The two conformal windows 707 and 708
enable the components within the turret payload device 706 to
transmit/receive beams while maintaining the aerodynamic characteristics
of the turret payload device 706.

[0073] The illuminator beam device is coupled to the turret payload device
706 in the path for the high energy laser beam 705. The illuminator beam
device detects atmospheric disturbances between the system 700 and the
target. The illuminator beam device detects the atmospheric disturbances
by actively illuminating the target to generate a return aberrated
wavefront through the first conformal window 707.

[0074] The coarse tracker 745 is coupled to the turret payload device 706.
The coarse tracker 745 is positioned parallel to and on an axis of
revolution of the off-axis telescope. The positioning of the Line of
Sight (LOS) axis of the coarse tracker 745 on the axis of revolution of
the off-axis telescope advantageously enables the coarse tracker 745 to
track the same target as the off-axis telescope while minimizing the
space within the turret payload device 706. The coarse tracker 745
detects, acquires, and/or tracks the target through the second conformal
window 708.

[0075] The auto-alignment system 735 is coupled to the turret payload
device 706. The auto-alignment system 735 includes one or more sensors
for detecting alignment of the beam. The auto-alignment system 735
communicates commands to the articulated secondary mirror 755 to modify
aiming of the high power laser beam and/or any other type of beam. The
auto-alignment system 735 communicates commands to the fast steering
mirrors 710 and 765 to modify the aiming of the high power laser beam
and/or any other type of beam. The auto-alignment system 735 can
advantageously communicate commands to the articulated secondary mirror
755 and/or the fast steering mirrors 710 and 765 to correct errors in the
aiming of the beam, thereby increasing the efficiency of the system while
reducing errors. Three angle sensors (not shown) sense an annular
auto-alignment reference beam, which originates from the auto-alignment
system 735. The annular auto-alignment reference beam is reflected off
the fast steering mirrors 710 and 765, the secondary mirror 755, and the
primary mirror 740.

[0076] The auto-alignment system 735 can close control loops that provide
the mirror translation solutions to the secondary mirror 755 and the beam
steering solutions to the fast steering mirrors 710 and 765. The
auto-alignment system 735 can bring the off-axis telescope 715 into focus
at the appropriate range along the axis of revolution and with the
correct line of sight. The auto-alignment system 735 can focus the
annular auto-alignment reference beam by utilizing the angle sensors. In
other words, when the beam is activated, the beam propagates along the
line of sight and is focused on the target at the correct range (i.e.,
the axis of focus of the telescope) and the coarse tracker 745 tracks the
target at the correct range.

[0077] The auto-alignment system 735 and/or the coarse tracker 745 can
communicate control signals to the turret payload device 706 for initial
and/or final pointing and steering direction to the target. For example,
the auto-alignment system 735 and/or the coarse tracker 745 can
communicate control signals to a first rotating mechanism (e.g., electric
motor, hydraulic arm, etc.) within the turret payload device 706 to
rotate the turret payload device 706 perpendicular to a nominal direction
of flight of the vehicle. As another example, the auto-alignment system
735 and/or the coarse tracker 745 can communicate control signals to a
second rotating mechanism (e.g., electric motor, hydraulic arm, etc.) in
one or more of the support arms 703a and 703b to rotate the turret
payload device 706 perpendicular to an azimuth axis of the turret payload
device 706.

[0078] The wavefront error sensor is coupled to the turret payload device
706 on the path for the high energy laser beam 705. The wavefront error
sensor determines an induced distortion of the aberrated wavefront of the
returning illuminator beam from the target based on a beam quality metric
for the target. In some examples, the wavefront error sensor communicates
commands to the articulated secondary mirror 755 based on the determined
induced distortion to reduce large, low order wavefront aberrations. In
other examples, the wavefront error sensor communicates commands to the
articulated secondary mirror 755 based on the determined induced
distortion to reduce residual tilts of the high power laser beam and/or
any other type of beam. The wavefront error sensor can communicate with
the articulated secondary mirror 755 and/or the fast steering mirrors 710
and 765 to remove bulk tilt and/or residual tilt, thereby advantageously
reducing aiming errors associated with the beam.

[0079] The IMU 760 is coupled to the turret payload device 706. The IMU
760 detects errors from commands communicated to the turret payload
device 706 based on an actual turret position. For example, the IMU 760
detects that the actual turret position is mis-aligned due to an
atmospheric disturbance between the turret payload device 706 and the
target. As another example, the IMU 760 detects that the actual turret
position is mis-aligned due to a course change by the vehicle.

[0080] The fast steering mirrors 710 and 765 are coupled to the turret
payload device 706. The fast steering mirrors 710 and 765 modify aiming
of the high power laser beam and/or any other type of beam based on the
detected errors. For example, the IMU 760 detects an error based on a
course change by the vehicle and the fast steering mirrors 710 and 765
modify the aiming of the high power laser beam to correct the targeting
based on the course change. The physical constraints of the turret
payload device 706 (e.g., size, configuration, location, etc.) can cause
the optical design of the off-axis telescope 715 to have a low f/number
design (also referred to as a "fast" design) (e.g., a f/number less than
f/1.0, a f/number less than f/2.0, etc.). The fast steering mirrors 710
and 765 and/or the secondary mirror 755 advantageously enable the system
700 to compensate for mis-alignments that can occur due to the low
f/number of the design. The fast steering mirrors 710 and 765 can correct
beam angle and translation. The secondary mirror 755 can correct
translations in the x, y, and z axes and/or can compensate aberrations
resulting from relative mirror tilts between the primary and secondary
mirrors of the telescope. The fast steering mirrors 710 and 765 and the
secondary mirror 755 can provide active aberration control.

[0081] The payload support ring 720 (also referred to as turret support
ring) is rotary coupled (e.g., direct mechanical connection, indirect
isolated connection, etc.) to the two support arms 703a and 703b. The
payload support ring 720 is attached to the payload device 706 via sets
of active isolator struts that de-couple the payload support ring 720
from the payload device 706, thereby eliminating the detrimental effects
of wind buffeting on the payload device 706, which can adversely affect
the beam's pointing accuracy. The de-coupled payload support ring 720 can
serve as the prime interface for the flexure mounted two-axis stabilized
structure that supports the primary mirror 740, the secondary mirror 755,
the coarse tracker 745, and the IMU 760. The payload windscreen shell 721
and 722 is in a shape of a truncated sphere having a flat side 722 and a
spherical side 721 on opposite sides of each other. The turret payload
device 706 is rotatable along an elevation axis over a first dimension
for deployment of the spherical side 721 (e.g., under an aircraft, on top
of a car turret, etc.) and is rotatable over a second dimension for
deployment of the flat side 722 (e.g., flush with a skin of an aircraft,
flush with the top of a car turret, etc.).

[0082] The coarse tracker 745 line of sight (LOS) 748 is co-linear with
the telescope's axis of revolution (the axis that passes through the apex
points of the primary mirror 740 and the secondary mirror 755). In other
words, the coarse tracker 745 and the off-axis telescope 715 are arranged
to minimize the space for the components within the turret payload device
706 and position the axis of revolution/coarse tracker LOS 748 as low as
possible in the turret payload device 706. An advantage to this
horizontal configuration of the coarse tracker 745 and the off-axis
telescope 715 is that the secondary window 708 is unmasked during
deployment at a minimum lookdown angle, thereby enabling the coarse
tracker 745 to identify the target of interest and/or to initiate an
auto-alignment sequence of operation.

[0083] As illustrated in FIGS. 7A-7B, the laser beam delivery system 700
includes a plurality of mirrors for directing a high energy laser beam
705 from an optical energy system (e.g., sensor system, laser beam
system, etc.) to the target. The plurality of mirrors includes a first
mirror mounted within the base and for receiving optical energy from the
optical energy system. The plurality of mirrors includes a second mirror
mounted within a top portion of the support arm 703a for receiving the
optical energy from the first mirror and for directing the optical energy
along an axis parallel to the support arm 703a. The plurality of mirrors
includes a third mirror mounted within a bottom portion of the support
arm 703a for receiving the optical energy from the second mirror and for
directing the optical energy through an opening in the turret payload
device 706 (part or all of the turret platform). The plurality of mirrors
includes a fourth mirror mounted within the in the turret payload device
706 for receiving the optical energy from the third mirror and directing
the optical energy to the payload device 706 (also referred to as turret
device). The secondary mirror 755 can be mounted within the payload
device 706 for receiving the optical energy from the fourth mirror and
for expanding the optical beam path from the fourth mirror. The primary
mirror 740 mounted with the payload device 706 is for receiving the
optical energy from the secondary mirror 755 and recollimating or
focusing the optical energy based on a beam application.

[0084] In some examples, the laser beam delivery system 700 includes a
Coude path to provide a path for the high energy laser beam 705 from the
base (the turret platform 702) via the support arm 703a to the target.
The fast steering mirrors 710 and 765 maintain the proper beam location
and orientation of the high energy laser beam through the Coude path to
the target.

[0085] In other examples, the primary mirror 740 collimates the optical
energy based on a target range. For example, the beam application is a
sensing application and the primary mirror 740 collimates the optical
energy based on a target range. In some examples, the primary mirror 740
focuses the optical energy. For example, the beam application is a high
energy weapon application and primary mirror 740 focuses the optical
energy.

[0086] In some examples, the payload device 706 includes an off-axis
telescope with a spherical mirror, a figure mirror, a conic mirror, an
on-axis telescope with central obscuration, and/or a refractive
telescope.

[0087] One skilled in the art will realize the invention may be embodied
in other specific forms without departing from the spirit or essential
characteristics thereof. The foregoing embodiments are therefore to be
considered in all respects illustrative rather than limiting of the
invention described herein. Scope of the invention is thus indicated by
the appended claims, rather than by the foregoing description, and all
changes that come within the meaning and range of equivalency of the
claims are therefore intended to be embraced therein.